Design method of virtual flight wind tunnel test model

Abstract

The invention discloses a design method of a virtual flight wind tunnel test model. The method comprises the following steps: (1) carrying out parametric modeling by utilizing three-dimensional CAD software according to wind tunnel test basic requirements of scaling, shape, strength, structure and function to obtain a flight wind tunnel test preliminary model; (2) selecting n design parameters from the model weight, the centroid coordinate value and the rotational inertia value, and respectively determining preset target values of the n design parameters; selecting n adjustable feature sizes from the internal space feature size parameters of the flight wind tunnel test preliminary model; and (3) adjusting n adjustable feature sizes by adopting a targeting method in the flight wind tunnel test preliminary model, and calculating n design parameters to enable the n design parameters to be equal to preset target values of the n design parameters. According to the method, the workload of design modification can be greatly reduced, and multiple design values such as the weight value, the rotational inertia value and the centroid coordinate value of the test model can be consistent with target values at the same time.

Description

technical field [0001] The invention belongs to the technical field of test aerodynamics, in particular to a design method of a virtual flight wind tunnel test model. Background technique [0002] Virtual flight wind tunnel test technology is an advanced wind tunnel test and flight performance evaluation technology. During the test, the scaled model of the aircraft research object can perform a certain range of multi-degree-of-freedom movements in the wind tunnel, and the specific degrees of freedom and movement range are related to the experimental research content. In the test, the test model is subjected to corresponding aerodynamic and dynamic effects in the flight environment simulated by the wind tunnel and the current flight state, and these two effects are also interacted and coupled. Under the joint coupling effect of aerodynamic force and dynamics, the attitude change of the test model within the allowable range can be measured and collected by the measurement sys...

AI Technical Summary

Problems solved by technology

Its disadvantages are: when adjusting the counterweight and size, there are a large number of adjustable parameters, which need to be modified based on experience. The adjustment process is often accompanied by a large amount of modification work, and the design workload is large; there are many design objectives, and it is difficult to meet all requirements: design It is necessary to meet the requirements of model weight, moment of inertia, and center of mass at the same time. Specifically, when it comes to the target value, the center of mass requirement includes 3 coordinate values. The general requirement of moment of inertia includes 3 spindle moment of inertia values, and even all 9 inertial matrix factors.

However, when there are many design target values, it is difficult for the usual design method to simultaneously achieve

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